Characterization of the Co-Flow Jet Effect as One of the Flow Control Devices

Julian, James W.; Iskandar, Waridho; Wahyuni, Fitri; Ferdyanto,; Bunga, Nely Toding

doi:10.35814/asiimetrik.v4i1.3437

Cited by 3 publications

(4 citation statements)

References 11 publications

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“…The initial step is determined by the ratio of grid variations and order values using equations ( 5) and ( 6). Next, determine the Grid Convergence Index (GCI), which is calculated using equations ( 7) and (8). There are two types of GCIs used.…”

Section: E Grid Independency Studymentioning

confidence: 99%

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Influence of Slat Size Variation as Passive Flow Control Instruments on NACA 4415 Airfoil Toward Aerodynamic Performance

Julian,

Anggara,

Wahyuni

2023

IJMEIR

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⎯ Airfoil is a fundamental geometry in designing various aerodynamic objects. Passive flow control installation is essential in determining the airfoil's aerodynamic performance. The influence of variations in slat size as a passive flow control instrument is analyzed using the CFD method with a Reynold number of = 6 Re 10 . In this study, NACA 6641 was seleceted as slat. The slat has two variations, i.e., 10% and 16% of the chord length. Based on the computational results, variations in slat size have a substantial influence on the aerodynamic efficiency of the airfoil. Variations in slat size additional Cl ability to reach 20.6043% and 13.1917%, respectively. In addition, a 16%c slat can delay a stall until it reaches AoA ≥ 19°. Meanwhile, a 10%c slat can delay a stall until it reaches AoA ≥ 17°. Variations in slat size also affect the drag force. Slat measuring 16%c can addition Cd up to 50.9252%. Meanwhile, 10% c slat additional Cd up to 21.8389%. Based on the resulting lift-to-drag ratio curve, a 10%c slat has the lowest lift-to-drag ratio compared to a 16%c slat. However, a 10%c slat has the highest level of stability when compared to a 16%c slat installation and without a slat installation.

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Section: E Grid Independency Studymentioning

confidence: 99%

“…Installing a slat around the airfoil's leading-edge is one of the passive flow control instruments. Slat installation has the property of suppressing fluid flow on the top side of the airfoil [4] - [8]. Therefore, the installation of slats as passive flow control has been developed to date.…”

Section: Introductionmentioning

confidence: 99%

Influence of Slat Size Variation as Passive Flow Control Instruments on NACA 4415 Airfoil Toward Aerodynamic Performance

Julian,

Anggara,

Wahyuni

2023

IJMEIR

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“…Boundary conditions in the domain consist of velocity-inlet and pressure-outlet. Meanwhile airfoil defined as wall (no-slip) boundary conditions [26].…”

Section: Mesh Domain and Setup Conditionsmentioning

confidence: 99%

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Julian

Iskandar

Wahyuni

2023

IJMEIR

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⎯ This research modifies the leading-edge structure of NACA 0015 and NACA 4415 to resemble the nose of a beluga whale. The focus of this modification is to improve the airfoil's aerodynamic performance and investigate the changing fluid flow patterns. Numerical equation used is RANS combined with the k-ε turbulence model. Mesh independence test shows that mesh with 200 elements is the best mesh. Validation results reveal that CFD data can follow the trend of experimental data, especially on the AoA before the stall. There was a significant increase in Cl from NACA 0015 and NACA 4415 at AoA>9°. On the other hand, the modification also had a positive effect by lowering the Cd value. The modification also provides an advantage by increasing the maximum Cl/Cd value. Furthermore, the separation point data shows that the modification can delay the separation of the fluid flow in the airfoil. Modifications can cause an increase in pressure on the lower side and a decrease in pressure on the upper side. Through velocity contours and streamlines, the modifications can reduce the recirculation area. Overall, modifying the leading edge has positive impacts on the NACA 0015 and NACA 4415 airfoils.

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“…This dimension is good enough and feasible to avoid computational domain effects. In general, the computational domain is given in Figure 3 [17]. Several computational parameters are given in Table 1.…”

Section: Detail Computationmentioning

confidence: 99%

Analysis of Aerodynamic Performance of Erosion Airfoil With Reynolds Number Variations

Julian,

Iskandar,

Wahyuni

2023

tekno

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Erosion on airfoil was investigated using computational methods to investigate changes in the performance of the airfoil. NACA 0015 used in this study has a chord length of 1 m, which is then used as a parameter in calculating the Reynolds number. The computational process is carried out with domain C with dimensions that have been arranged in such a way as to avoid the influence of the boundary on the computational results obtained in this study. The governing equation for this study is RANS which the standard k-ω turbulence model supports. Erosion has a considerable influence on changes in the aerodynamic performance of the airfoil. Erosion can significantly reduce the Cl value of the airfoil, especially at high AoA. Erosion of the airfoil results in an increase in the value of Cd. The increase in Cl value can be explained by visualizing the pressure contour around the airfoil. The pressure contour shows a decrease in pressure in the lower but an increase in the upper. The velocity and streamline contours can explain the cause of the increase in Cd, which is very clearly caused by the separation in the erosion area and on the upper surface of the airfoil.

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Characterization of the Co-Flow Jet Effect as One of the Flow Control Devices

Cited by 3 publications

References 11 publications

Influence of Slat Size Variation as Passive Flow Control Instruments on NACA 4415 Airfoil Toward Aerodynamic Performance

Influence of Slat Size Variation as Passive Flow Control Instruments on NACA 4415 Airfoil Toward Aerodynamic Performance

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Analysis of Aerodynamic Performance of Erosion Airfoil With Reynolds Number Variations

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